|Publication number||US3091077 A|
|Publication date||May 28, 1963|
|Filing date||Dec 29, 1960|
|Priority date||Dec 29, 1960|
|Publication number||US 3091077 A, US 3091077A, US-A-3091077, US3091077 A, US3091077A|
|Inventors||Bruce G Erickson, Adam J Henriksen|
|Original Assignee||Nordberg Manufacturing Co|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (6), Referenced by (21), Classifications (6)|
|External Links: USPTO, USPTO Assignment, Espacenet|
May 28, 1963 B. G. ERICKSON ETAL 3,091,077
ENGINE CONTROL Filed Dec. 29, 1960 2 Sheets-Sheet 1 DE! VE N GER GAS HEAER if jf /6 INTAKE /5 MAN/FOLD GAS '/Z [HEADER )Jip 7 FI/Z9r lf fr@ lr lr ,0^ 7 Egfjgf/T a y UPERCHARGER A e Z3 @OVERNP/ V0 4 INTAKE /02 MAN/Pow /f? .SY/ppl y INVENTOR BY Parier KE/'fer //ar/ffyf.
3,6%,977 ENGINE CONTROL Bruce G. Erickson and Adam J. Henriksen, South Milwaukee, Wis., assignors to Nordberg Manufacturing Company, Milwaukee, Wis., a corporation of Wisconsin Filed Dec. 29, 1964i, Ser. No. 79,410 29 Claims. (Cl. 60-13) This invention relates generally to internal combustion engines and more particularly to .a control system for regulating and coordinating air and fuel requirements in a supercharged internal combustion engine. It also relates to a method of regulating vand coordinating air and fuel pressure in a supercharged engine.
With conventional exhaust driven supercharging systems, engine air requirements are ordinarily not met during starting operations since little or no energy is available to drive the turbocharger during this period. The result- `ant lack of inlet air header pressure is not too important in four cycle engines, which are self-breathing, unless such an engine has a locked in torque, but -two cycle engines require sufficient header pressure for proper scavenging after the engine has red initially. Without blower supplied air the cylinders are not adequately scavenged of combustion products.
Starting an internal combustion engine of the gas fuel type is further hampered by uncontrolled gas pressure in the cylinders when tiring does not take place immediately. For example, as the engine is turned over by the starting motor it is not unusual for several revolutions of the crankshaft to take place before ring actually occurs. During this period gas is normally pumped into the cylinders just as though tiring were actually taking place and consequently gas over flows into the exhaust header Vand muffler. As a result, exhaust header and muffler explosions frequently occur.
The operating eiciency of a supercharged internal combustion engine also varies substantially under varying load conditions once an engine is started. This is particularly true of two cycle engines of any fuel type. In a supercharged two cycle engine at lower loads and idling under no load, insutcient energy is supplied from the exhaust header to drive the turbocharger and consequently insufficient scavenging air reaches the `air intake header. Actually, of course, some scavenging air is supplied, but the amount required ordinarily far exceeds the amount supplied. It is common practice to provide a separate motor driven until or a crankshaft driven blower to provide additional air for scavenging at low loads and idling.
Sudden load bump also tends to upset the equilibrium between air and fuel requirements in a supercharged internal combustion engine. This is true in both two and four cycle, gas, diesel and dual fuel engines. It is easy to see what the ordinary result of suddenly throwing a heavy load on a supercharged engine might be. Because of the ywheel elect of the turbocharger, the blower output will lag behind actual engine load. The fuel, be it diesel or gas, will at the same time be supplied by governor control according to the actual load on the engine. Under these circumstances, it will be obvious that the inlet -air pressure will be too low. The result is an exceedingly rich mixture in the cylinders. In ya diesel engine this rich mixture will only partially yburn and result in billows of black smoke in the exhaust. In a gas engine, however, a rich mixture will not hre at lall and the engine will ordinarily quit.
It is accordingly a primary object of this invention to provide a composite control system for efficiently regulating and coordinating air and fuel requirements in a supercharged internal combustion engine.
ariston' Patented May 28, 1963 Another object is a control system including automatically regulated means for supplying an -air jet assist for a turbocharger during engine starting.
Another object is a control system -for Iautomatically regulating gas pressure in two and four cycle gas fueled engines and preventing exhaust header and muler explosions.
Another object is a control system including load responsive compressed air means for assisting turbochanger operation at idling and low loads.
Another object is means for assisting turbocharger operation `at idling and low engine loads which eliminates .the need for engine driven or auxiliary blowers.
Another object is a control system including automatically controlled air jet assist means for supplying additional energy to the turbocharger to maintain proper air-fuel ratios during load bump and rapid engine acceleration.
Another object is a control system for supercharged internal combustion engines which automatically regulates air and fuel requirements as a function of air intake header pressure.
Another object is a control system including means responsive to gas header pressure and air intake header pressure for providing automatic air jet assistance to a turbocharger during engine acceleration.
Another object is a control system including means for automatically regulating gas pressure during load bump and engine acceleration to coordinate it with lair manifold pressure.
Another `object is a control system including means for shutting olf all air jet assistance to a turbocharger when a predetermined air inlet manifold pressure is reached.
Another object is a control system including means vfor establishing maximum permissible gas pressure and jet assistance air pressure.
Another object is a method of regulating and coordinating air and fuel requirements in a supercharged internal combustion engine.
These and other objects will be found in the following specification and claims wherein like reference numerals identify like parts throughout.
The invention is illustrated more or less diagrammatically in the drawings wherein several variations of the control system are shown:
FIGURE l shows the composite gas pressure and air inlet pressure control system,
FIGURE 2 shows the system limited to gas pressure control,
FIGURE 3 shows the system limited to air jet assistance control, and
FIGURE 4 shows the system of FIGURE 3 further limited to air jet assistance control during load bump and acceleration.
FIGURE l illustrates a composite gas pressure and inlet air pressure control system as applied to a supercharged internal combustion engine 2. The engine shown is gas fueled and spark tired but it will be understood that this system might be adapted to diesel and dual fuel engines as well. Similarly, for purposes of explanation, engine 2 will be described as a two cycleengine though the system is also adaptable for use with four cycle eng1nes.
Engine 2 includes crankshaft 3 and ywheel 4. The individual engine cylinders, indicated diagrammatically at 5, receive gaseous fuel through gas header 6`from fuel line 7. Fuel line 7 is connected to a conventional source of gaseous fuel (not shown). An engine gas control Valve 9 is operatively associated with fuel line 7. Governor 10 regulates Valve 9 as a function of engine load in a well-known manner, and can be pre-set by the ena jet assist cut-off valve 67.
gine operator. Also operatively associatedwith fuel line 7 is a secondary gas pressure valve 12.
An inlet air manifold is connected to the engine fcylindersS for delivering air under'. pressure from a conkventional exhaust, driven turbocharger 16.
In a Wellknown manner, the engine exhaust feeder (not shown) turbocharger.
A compressed air pipe 18 extends to the exhaust driven turbocharger 16 and is adapted to direct a jet of corn- ,pressed airV to the turbine. Interposeld in the air line -18 is acontrol valve 2,0 for regulating lthe amount `of air jet assistance provided the turbine,of the turbocharger 16. YTlriersecondary gas pressure -valve 12 and-,the air jet assist control valve 20 are regulated ask a function of gas pressure in the gas header` or Yair vpressure in the air inlet manifoldV or a rcornbination of theY two. Anl air pressure Ysignal drawn from air supply line ,18' regulates the -.valves' \1=2 and A2(} through the'rmedium ofeaY seriesof intermediatei-control-valves, shownrgenerally at 22, and made responsive to g'as header pressure and `inlet air manifoldpressure. A signal'airpressure llimiting valve 23 is interposed in this network. v Y
Secondary gas pressure Valve 11.2 includes a split valve chamber 25`opened and closed by valve operator 26.
Valveoperator is. connected to adaphragm 27 interposed in bell .enclosure 28. A .pilot air lsignalichamber `29 is formed in bell enclosure 2S bydiaphragm 27.. -The diaphragm and valve .26 arebiasedtowardsclosed posi- The valve operator 34 by 'coil 'springs 3S'and 39 on opposite sidesof the -diaphragm. This Vvalve open-position is veiected .when no pilotvair vpressure is present Ythe chamber `37. Pilot air signal-inlet port 40 'is 'provided'in chamber '3;7.
The intermediate` control ,valves 22`includ`e a gas bias relay valve`45. `Gras biasrelay valve 45 includes a split Yvalve 'chamber 46 having a valve `operator V47 extending thereinto. Valve ofp`erator4l7 isY connected to diaphragm 48 whichtformsone wall of an air manifold signal chamber I49. The valve operator `47, ,When'no airrnanifold Apressure Visipresent in chamber 49, is balanced byra pair of coil springs 50 and' 51 vto maintain a predetermined valve opening. VPilotair signal inlet port 52 and outlet port 53 are formed in the valve chamber 46. Air mani- ,fold signal inlet Vportj5'4 is formed ,in chamber 49.
Y Another of the intermediate'valves 22 is jet assist bias k relayvalve` It is substantially Aidentical in construction to relay valve 45. YalvejSS includes a split valve chamber 56, valve operator 57, diaphragm 58, air manifold signal chamber 59, balancing springs 60 and 61, air manifold Vsignal inlet port'62, pilot air signal inlet port 6,3 Vand pilot airpsi'gnal outlet kport 64. Coil springs v`.60 and V651 halanee'diaphragm-,SS and consequently valve 'operator 57in Aap'osition Vcalculated to permit a predetermine'd air fsignal passage to the rvalve outlet port'64 under predetermined conditions. v
Thje series of intermediate valves V22, further includes let assist cut-oirr valve 67 includes. a split valveY chamber 68.V Valve actuator 69 extends into valve, chamber 68 and is opera-tively connected .to aV diaphragm 7.0v :forming one wall of the air manifold signal chamber 71. A coil spring 72 normally biases actuator 69-intothe position yshown in FIGURE 1, closing off communication between valve chamber 68 `and pilot 4air signal inlet port-73. Another pilot air signal inlet port is indicated at 74 and a pilot air signal outlet port is indicated at l75. Adair vmanifold signal inlet port 76 i-s formed in the chamber 71.
-is connected to drive the turbine of theeXhaust driven formed 'in valve charnltaerv 81. A`port59 is Aformed'in the chamber 84 rand gas pressure signal -inlet port 90 is formed in chamber 35.
The remaining intermediate valve in the series 22-is indicated generally at 80. Valve 80' might be referred to yas an acceleration control valve and includes a split valve chamber 81. Valve actuator S2 extends into chamber 81 and is operatively connected at its opposite end to diaphragm 83. An air manifold signal chamber 84 Vis formed on one side of the diaphragm 83 and a gas pressure signal chamber 85 formed on the other side. The diaphragm `and consequently the actuator 82 are normally -biased towards a valve open position by coil spring 86. vUnder generally constant engine load conditions,V the valve will -be in the position Vshown in FIGURE 1. Pilot air signal inlet port 87 and outlet port 8S are Air manifold signalV inlet An ,operating medium for the system inthe formpf pilotfair pressure is tapped'oithe'main airline1'8. In
Athe alternative, itmightbe'taken directly from la Vcrimlpressed air source. The pressure sourceimight .be an 'air'tank supplied by -a'conventional air compressor. The air compressor in turnrnightbe driven byerrgine 2for predetermined periods of"time under optimum-load conditions to build the tank pressure up to ZSOtto 300 `p.'s.i.,
for example, at which point an automatic'cut-ol'would stop the compressor. This method of maintaining an air pressure source is only 'an example', however, and 'any means of supplying compressed Vair might "be utilized. 'The high pressure compressed Vair at 'the source is reduced toa much lowerV working pressure'for both the pilot lines and the main airline, however. Y
As Vwas set lout above, pilot airtfor the system illus trated in 1 is tapped from the main line The pilotline 91 extending ltherefromhas :a signal pressure regulator valve 23 interposed therein. Y Valve 23 includes a split valve'cham'ber 92 and a valve aetuator 93 operatively connectedfat one Hend .to diaphragm 94. Under atmospheric conditions, @the coil spring SSbiases `diaphragm .94' and .consequently 4actuator Vtowards a valveopen position. Valvechamber 92 Vis in communication .Withdiaphragm 94. Diaphragm .94.and valve actuator 93are Vthus controlled by the'pres-sure'in Valve chamber 92. Consequently, it will be obvious Ythat by mak- "ing .the coilispring 95 .adjustable so that it may be set to a.p'r'edetermiried strength, thermaximumpressure in pilot r Yline 9.1 can becontrolled.
l Pilot -line 91 lhas a T-'branch 100` at one end. The 'lf-branch 100l communicates withpilot airsignalinlet port 52 in gas ybiasrrelay valve 45 and with `pilot Aair signal inlet-port 63 injet assist bias relay valve 55. A'branch vline Yllvlconnects pilot line l91 Withpilot air signal inlet port 73 in jet assist cut-off valve 67. .j
s Pilot air signal -outlet port 53of gas bias relay valve A45 is connected through pilot line 102 to pilot air signal inlet port 31 4of secondary gas pressure controlvalve 12.
Pilot jline 10'5 connects .pilot air signal outlet port 64 of jet assist bias vrelay valve 5'5 with pilot air signal "inlet port 74 ofjet assist cut-olf valve467. Pilot line 106 in turn connects pilot air signal VVoutlet port 75 -of jet Vassi-st cut-oir valve 67 with pilot air signal inlet port 87 Vvof acceleration control valve l80. Pilot lair signal outlet port S8A of acceleration control valve 80 is'in turn connected' through pilot line 107 to pilot air signal inletpo 400i ai-r jet -assist control valve 20.
Each-of the series of Yintermediate control valves .22Jis operatively' connected'to and responsive `to the pressure -in inletfair manifold 15 also. This relationship isfacilitated by manifold pressure Apilot line connected to manifold 15 at 111 and at its other end to signal inlet port 89 vin acceleration control valve 80. -A lbranch air manifold pressureV -pilot line 112 connects signal inlet. 'por-t' 54 -in -gas `bias relay valve 45 with Vpilot line 110.
In turn, branch air vmanifold pressure pilot line -113 is connected to signal inlet port y62 of jet assist bias relay valve 5S and branch 114 is connected to Signal inlet port 76 of jet assist cut-oif valve 67.
Acceleration control valve `80| is also responsive to gas header pressure and this response is lfacilitated by gas pressure pilot line 118 connected at 119 to gas header 6 and at its other end to gas pressure signal inlet port 90 of acceleration control valve 80.
FIGURE 2 shows the system for use with a gas engine in which only gas pressure control is desired. Only a gas pressure control valve 12, a gas bias relay valve 45 and an air signal pressure regulator valve 2y would be necessary. These valves could be identical in all respects to those in FIGURE 1. The pilot line network could be simplified. For example, a single air manifold pressure pilot line 112 would connect inlet air manifold 15 with signal inlet port 54 in gas bias relay valve 45. Pilot line 91 would lbe connected directly to air signal inlet port 52.
If gas pressure control alone is not desired, the system might be modified as in FIGURE 3. rlf'he secondary gas control valve 12 and gas 'bias relay valve 45 along with their associated pilot line connections could lbe eliminated. The system could otherwise be identical to FIG- URE 1.
It should be understood that the load responsive system described hereinabove could 'be made responsive to any load `factor and is not necessarily restricted to gas pressure. 5
FIGURE 4, on the other hand, illustrates an inlet air pressure control system wherein only load bump control or engine acceleration control is desired. Here, the system has been modified to eliminate secondary gas control valve 12, gas bias relay valve 45, jet assist bias relay valve 55 and jet assist cut-olf valve 67. All that remains is the acceleration control valve 80 and pilot air regulator valve 23 along with air jet assist control valve 20. The network of pilot lines remains substantially the same with air pilot line 91 being connected directly to air signal inlet port S7 in acceleration control valve 80. As before, load sensing can be done other than by gas pressure.
The use and operation of this invention is as follows:
The control system embodying this invention is best described as applied to a supercharged two cycle engine of the gas fueled type. To graphically relate the various functions of the system under pertinent engine operating conditions, the use and operation is best described by beginning with the starting operation of the engine itself.
4Immediately prior to starting the engine, the operator opens the main air line 1S and consequently the pilot line 91 to the source of pressurized air,
At this time, the gauge gas pressure in manifold 6 will be zero as will gauge pressure in inlet air manifold 15. Each of the intermediate valves 2.2 has been constructed to establish a predetermined valve Opning under these conditions. These openings in turn affect the pressure of the air signal delivered through the intermediate valves to air jet assist control valve 20 and secondary gas control valve 12.
The regulation of a secondary gas control valve 12 is affected by the valve opening in the gas bias relay valve 45. This opening is in turn determined solely by air pressure in the air inlet manifold 15. When the engine is started, it will be seen that there is no air inlet manifold gauge pressure; however, a gas supply is needed. So when the operator establishes the fuel rack setting to begin fuel feed to the gas header for starting the engine, the secondary gas control valve 12 must be open to a certain extent to allow a predetermined gas pressure to be established in the gas header. With a zero pressure signal in inlet manifold signal chamber 49 of gas bias relay valve 45, balancing springs 50 and 51 permit a minimum air signal to be delivered to air signal chamber 29 in secondary gas control valve 12. This minimum signal causes valve '12 to establish a gas pressure in the gas header. A s a remane?? sult of controlling` gas pressure in this manner, when the engine turns over prior to starting excess gas pressure will not build up in the cylinders and cause gas overow into lche exhaust header and muffler where exhaust header and muffler explosions then frequently occur.
As the engine starts, the air pressure in the air inlet manifold 15 due to exhaust energy and also to jet assist, which will described hereinafter, increases and this signal causes the bias relay valve 45 to put an increasing air signal to regulator valve 12 which consequently affects the delivery of gas to the engine at the same pressure as the pilot signal it receives. Furthermore, the balancing springs 50 and 51 of gas bias relay valve 45 and internal areas can be pre-set so that gas pressure is ratioed as a function of inlet air manifold pressure. For example, if the relay valve Were ratioed at 2, with a signal calculated to provide 1.5 p.s.i. of gas pressure when air inlet manifold gauge pressure is zero, when the air inlet manifold gauge pressure gets to 5 p.s.i., the signal to secondary gas control valve 12 would be 2. times 5 p.s.i. plus the original 1.5 p.s.i. bias or 10 p.s.i. plus 1.5 p.s.i. which would be 11.5 p.s.i. air signal. It will thus be seen that virtually any gas pressure-air manifold pressure relationship might be eifected.
J et assist bias relay valve 55 normally controls the air signal to the jet assist control valve 20. yBy normally is meant that under certain abnormal or otherwise specific operating conditions, overriding intermediate Valves take over from the air jet assist bias relay valve 55. These certain operating conditions will be discussed hereinafter.
As will be seen from the position of the intermediate valves 55, 67 and 80 prior to starting of the engine and with the inlet air manifold gauge pressure and the gas header gauge pressure at zero, the valve S5 is open, valve 67 is closed to branch air signal line 101 and open to air signal line 106 and valve 80 is open. The amount to Which valve 55 is open is pre-set by the relative Strength of the balancing coil springs 6,0 and 61. With the Valve open to the position shown in FIGURE 1, a minimum sigv nal from pilot line 91 courses through valve chamber 56 in Aand idling and thereafter under increasing loads, the
pressure in inlet air manifold 1S increases and, with this increase in pressure, ,air jet assist relay valve 55 is con- Y 'structed to open proportionally further to permit an increasingly larger signal to lbe delivered to'iair jet assist control valve 29. As the signal to the air jet assist control valve in Ceases, valve 2t) closes generally pro portonally and permits a lesser and lesser amount of air jet assistance to reach turbocharger 16. Thus, it be seen that. at low loads and underidling conditions, a large amount `0f ist assistance is. provided the turbocfharger, as there is `during starting ofthe engine. Proper scavenging is Consequently insured during these periods with reresultant eicient engine operation.
When the air inlet manifold pressure reaches a certaih predetermined gure, jet assist cut-off valve 67 takes over shutting off air signal inlet port 74 in valve 67 and opening ar signal inlet port 73. The result, as he readily seen, is to by-pass jet assist relay valve 55 and send the air signal from pilot line 91. directly through ist assist Cut-Ofi valve 67 and acceleration control valve 80 to jet assist control valve 20, As a result of this "hiphop" sought by charger' 16 once this predetermined by-pass' pressure is reached. t The'elect is to provide a limiting pressure above which normally-air jet assistance is not provided the engine. The desirability of this is easily Iunderstood since vunder normal steady load conditions in the h-igher vrange the turbocharger is completely self-sustaining. No Yair jet assistance is needed to aid the turboeharger in pro- 'viding the pre-calculated proper air manifold pressure 'called for by the engine.
Under certain conditions, however, generally at medium and high loads, air jet assistance is required for turbocharger 16. These conditions are found when a load ,bumJp-is felt by the engine. That is, when a heavier Aload is suddenly thrown on the engine. This causes the Y Yspeed responsive governor 10 to immediately seek to 'supply a greater amount of fuel to the engine. Since the 'turbooharger must overcome its flywheel effect, it does not send additional air to the inlet air manifold as rapidly as fuelV is received by the gas header. Consequently, in gas engines an over rich mixture results and the engine often dies. To remedy this'situation an acceleration control Avalve 80 is provided. Control valve 80 is made responsive toboth gasheader pressure Vand inlet air manifold pressure and is balanced to be wide open Wheninlet lair manifold Vpressure and Vgas headerpressure maintain a predetermined balance. 'I'his valve relationship is controlled by setting the strength of the coil spring 86 in acceleration control rvalve 80. kWhen the v'balance between the inlet air manifoldpressure and the gas header pressure as signaled to the acceleration control valve 80 by pilot lines 110 and 11118, respectively, is upsetin 'such a manner that `gas header pressureishigher by a certain amount'than'inlet air manifold pressure, the acceleration control valve 80 respondsby closing .as a function of this pressure differential and asa consequence air jet'assist control 'valve 20 opens as a function of the differential. As valve opens, of course, air jet'assistance'is provided turbocharger 16 and this in turn builds or tends to buildup the pressure -in inlet air manifold 15.
With the build up of inlet air manifold pressure, lche original balanced relationship between gas header-pressure and inlet air manifold pressure tends to'be re-estab- Ylished and acceleration control valve opens to increase the signal sent to lair jet assistV control valve 20 and consequently cause it to close. By virtue of this unique combination of'valves, maximum 'engine eciency is'maintained even during periods when sudden loads are thrown luponthe engine and gas fueled engines arenot subject to over rich mixtures which result inthe engine dying.
4Of course, as applied to diesel Yengines the over rich mix- VVture is also'eliminated and withit objectionable heavy black smoke inthe exhaust.
To assist'the re-'establishmentof the balance between I'air'inlet manifold pressure and gas header pressure when the acceleration control valve does not respond quickly `enoughto'immediately completely overcome the unbalance, the gas Vbiais relay valve y45 tends to hold down "glas pressure. This permits the inlet air manifold pressure' to catch up with the gas header pressure more rapidly. Gas 'headerpressure is held down by relay valve 45 in this manner since the manifold pressure to which it is respon- `sive does not 'immediately increase to a degree consistent *with the `higher power-setting called for by governor 10.
In a sense, what the engine has is both a belt and suspendl ers.V Theacceleration control valve 80 causes air jet assistance to be delvered to the turbocharger under sudden acj lce'leration .conditions while the gas bias relay valve 4S .tends to. hold the gaspressure down to facilitate re-estabilishment of the predetermined balance yas this balanceis the air jet assisted turbocharger.l
A Pilot pressure regulator valve 23 in pilot line 91 vis placed there primarily to limit maximum gas pressure. It accomplishes this since it'limits the supply of -signal .air for gas'pressure relay valve 4S. No matter what gthe inlet air manifold pressure, a maximum signal `operation of lan engineof this type.
other than -a carburating gas valve is utilized.
23. This gives automatic overload engine protection by limiting maxmum fuel supply. The regulator valve 23- also limits the lsignal pressure available at Vair'jet Vassist control valve 20, but its function is not as important in this case since valve 20 would ordinarily be already closed when such a signal is reached.
Under certain circumstances, it might be desirable to provide a modified system which provides control over only gas header pressure. This could 'be the case because of specific operating conditions under which the engine is utilized or for economic reasons or otherwise. Such Va modied system is illustrated diagramm'atically in FIG- URE 2V of the drawings. In the control systemshown in FIGURE 2, an air pressure signal to a secondary'gas control valve 12 is regulated by gas bias relay valve 45 responsive to inlet air manifold Vpressure in the same manner described in the use and` operation of the .composite system illustrated in FIGURE l. A-pilot air pressure regulator valve-23 in the pilot line 91 acts as a pressure-limiting control and, as in the system of FIGURE l, might be pre-set at a 20` p.s.i. maximum. The system of FIGURE'Z .provides a gas pressurelimiting system directly responsive to air inlet manifold pressure. As a result, excessive gas pressure does notbuild up in the gasY header causing overilowinto the exhaust header and mullier with its concurrent danger of muffler-,and exhaust header explosions.
Sometimes it is desirable to operate an engine of this type with only a jet assist control system, eliminating the gas pressure regulation. A control system adatped to perform only the foregoing function is shown in FIGURE 3 of the drawings. The control system illustrated in YFIG- URE 3 is identical to that shown and described in FIG- URE l with the exception that it eliminates the -gas bias Y relay valve 45 and the secondary gas control valve 12 and their'functions. l et assist relay valve 55, jet'assist cut-off valve 67 and acceleration control valve 80 remain in the intermediate control valve series. They function exactly as described in the operation of the composite system'of yFIGURE l. In view of this, it is thought that no detailed explanation of their use and operation is necessary'to the understanding of this modication of the system-'embodying this invention. Suice it to say that air jet assist and control is provided at engine starting, idling and low loads and during periods of acceleration when the'engine suffers load bumpf In some instances, Vionly ya load bump and acceleration control jet assist system is necessary to the e'icient Such a control sys- Item lis illustrated diagrammatically in FIGURE 4 of the drawings. VHere, the only'valves required are the air jet assist control valve 20, the acceleration control valve and the pilot air regulator valve 23. The acceleration control valve 80 is responsive to both gas header pressure and inlet air manifold pressure in the same manner that'the acceleration control valve is inthe com- -posite system illustrated in FIGURE l and described above. The efficiency of operation obtained is consequently'identical to that described in the explanation of -use and operation of the aforementioned composite system. The flywheel effect of the turbocharger 16 is countered by air jet assistance provided the turbocharger when it lags the engine ygas pressure input due to load bump and acceleration. As a result, undesirably rich mixtures are substantially prevented, eliminating engine ystoppalges and ineliicient utilization of fuel in Vboth gas land diesel engines. l t
'I'he systems of FIGURE lfFIGURE 3 and FIGURE 4are also adaptable to'engines wherein vgas feed means IIn such case, the load upset signal to the Aacceleration control "valve adapted'toprovide airjet assist during load"bump 9 might be taken `from the load signal on the governor of the engine.
Although the control system embodying this invention has been described as -applied to a two cycle gas red engine, it is, `of course equally `applicable under many circumstances to four cycle gas red engines and also to two and four cycle diesel and dual fuel engines. Of course ythe gas pressure control portion of the system would not be ladvantageous alone in conjunction with a diesel engine, but the system Vas a whole in all other instances would contribute to engine eliiciency and safe and continuous operation.
It will be understood that the foregoing description of the system embodying this invention is illustrative only and many changes might be made without departing from the theme thereof. Accordingly, it is not intended that the description be denitive and the invention should be limited yonly by the scope of the appended claims.
1. A system for regulating and coordinating inlet air pressure in an engine having an exhaust driven turbocharger -supply-ing air to au inlet manifold and a fuel header comprising auxiliary means for supplying additional energy lfor driving the turbocharger, and means responsive .to fuel header pressure and inlet air manifold pressure effective to actuate said auxiliary means to -supply energy to the turbocharger when a predetermined balance between said fuel header pressure and said inlet air manifold pressure is upset by a sudden load being thrown upon the engine.
2. The system of claim 1 further characterized in that said auxiliary means comprises compressed air means.
3. The structure of claim 1 further characterized by and including means for energizing the auxiliary means so -that additional energy will be supplied to the turbocharger during starting and low loads.
4. ri`he structure of claim 1 further characterized by and including means for limiting the rate of supply of fuel when a rapid load increase is yapplied to the engine.
5. The structure of claim 1 further characterized in that said last-mentioned means is constructed to limit the fuel supply as a function of inlet manifold pressure during engine operation.
6. A system for regulating and coordinating inlet air pressure in an engine having a fuel header and an exhaust driven tu-rbocharger supplying air to an inlet manifold comprising auxiliary means for assisting the turbocharger, and means responsive to inlet manifold pressure and to gas header pressure to lactuate said auxiliary means when a predetermined balance between said gas pressure and said manifold pressure is upset by sudden load being thrown on the engine during operation.
7. A system for regulating and coordinating inlet air pressure in an engine having a fuel header and an exhaust driven turbocharger supplying air to an inlet manifold, comprising auxiliary means for assisting the turbocharger, means responsive to air inlet manifold pressure effective to actuate said auxiliary means when said manifold pressure is below ya predetermined pressure, other means responsive fto inlet manifold pressure, said other means also being responsive rto fuel header pressure, said other means effective to actuate said auxiliary means when a predetermined balance between said fuel pressure and said manifold pressure is upset by an increased fuel supply being delivered to said header as a result of a sudden lload being thrown on said engine.
S. The system of claim 7 further characterized by and including means responsive to air inlet manifold pressure effective Ito shut off said auxiliary means when a predetermined manifold presure is reached during engine operation.
9. A system for regulating and coordinating inlet air pressure in an engine having a gas header and an exhaust driven turbocharger supplying air to an inlet manifold comprising air jet means for driving the turbocharger, an
air jet control valve associated with -said air jet means for actuating and shutting off said air jet assistance, a source of compressed air, means for carrying signal air pressure from said source to said "air jet control valve, -said air jet control valve being responsive to a maximum signal pressure to shut off said air jet assist means and being responsive to a minimum signal pressure to actuate said air jet assist means, a jet assist relay valve connected to said signal pressure carrying means, said relay valve being responsive to inlet air manifold pressure, said relay valve being effective to cause said minimum signal to be delivered to said air jet control valve when inlet yair manifold pressure is below a predetermined pressure and cause said maximum signal to be delivered to said air jet control valve when said inlet air manifold pressure is above a predetermined pressure, a jet assist cut-off valve connected to said signal pressure carrying means, said jet assist valve being responsive to inlet air manifold pressure, said cutoff valve means being efective to cause said signal to bypass said relay valve when said inlet air manifold pressure reaches a predetermined pressure, an acceleration control valve connected to said signal pressure carrying means, said acceleration control valve being responsive to fuel header pressure and inlet air manifold pressure, said acceleration control valve being effective to permit a maxfmum signal to be delivered to said air jet control valve when a predetermined balance is maintained between said fuel header pressure and said inlet manifold pressure, said `acceleration control valve causing a -m-inimum signal to be delivered to said air jet control valve when said balance is upset by fuel pressure increasing due to an increased load suddenly being thrown upon said engine.
1G. A method of controlling the air and gas supply in an internal combustion engine having an exhaust driven turbocharger supplying air to the air inlet manifold, comprising the steps of providing an auxiliary turbocharger drive means, sensing the air inlet manifold pressure, sensing the gas pressure in the gas header, actuating the auxiliary means when a predetermined balance between gas pressure and air inlet manifold pressure is upset by a rapidly increasing load being thrown on the engine causing the gas pressure to increase relative to the inlet manifold pressure, and holding the gas pressure down as a function of air inlet manifold pressure to tend to maintain a predetermined balance between air inlet manifold pressure and gas header pressure.
11. A system for maintaining an approximately constant air-fuel ratio in an engine having an exhaust driven supercharger supplying air to the engine anda source of fuel, comprising auxiliary means for supplying additional energy to the supercharger in addition to the exhaust energy received by it from the engine, and means responsive to an unbalance between the inlet manifold pressure and the rate of fuel being supplied )to actuate the auxiliary means when the engine is subjected to a rapid load increase.
12. The structure of claim 11 further characterized in that the source of fuel is gas and the unbalance responsive means is responsive to the relationship between inlet manifold pressure and gas pressure. 60
13. The structure of claim tll further characterized by and including means for limiting the rate of increase of Ithe fuel supply when a rapid load increase is applied to the engine.
14. The structure 4of claim 1l further characterized in that the auxiliary means includes a source of air under pressure connected to the supercharger.
15. The structure of claim 1l further characterized by and including means for energizing the auxiliary means to supply additional energy to the supercharger during starting of the engine Iand at low loads.
16. The :structure of claim 15 further characterized by and including means for cutting off lthe energizing means when the engine has reached a predetermined load so that thereafter, as load increases, the auxiliary means will not supply additional energy to the supercharger.
17. The structure ofl claim 11 further characterizedin that said last-mentioned means is constructed to limit the fuel supply as a function of inlet manifold pressure Vduring engine operation.
18. A method of maintaining an approximately consta-nt air-fuel ratio mixture in the cylinders of an engine supplied with gaseous fuel :and having an exhaust driven supercharger, including the steps of providing an auxiliary source of energy for the supercharger capable of supplying energy to the superchanger Vin addition to the energy it receives from the exhaust gases, sensing the pressure Vof the air in the Aengines inlet manifold, sensing the pressure of the gas in the gas header, establishing `a balance between the inlet air pressure and the gas pressure corresponding to'a theoretically proper `air-fuel ratio, and energizingr the auxiliary source of'energy so as -to supply aditional energy :to the isupercharger when the balance between iniet manifold pressure and kgas pressure is upset due to a rapid load increase on'the engine.
19. A method of maintaining an approximately constant air-fuel ratio mixture in'an 'engine `having an exhaust driven supercharger supplying air to the engine and a source for fuel, including the'steps of providing an auxiliary source of energy for the superchargerr capable of supplying energy to the supercharger in addition to the energy it receives from the exhaust, gases, sensing the pressure of the air in the engines inlet manifold, sensing the rate iat which fuel is beingsuppli'ed to the engine, establishing a balance between the inlet' air pressure and the fuel rate corresponding to a theoretically proper airfuel ratio, and energizing the .auxiliary source of energy f to supply additional energy to fthe -supercharger when the balance between the inlet manifold pressure `and the fuel rate is different from lthe Vbalance representative of the theoretically proper air-fuel-ratio.
20. The method of claim 19- further characterized by and including the step of using a gaseous fuel, and establishing 'a balance between the inlet air pressure iand the gas fuel pressure corresponding to a theoretically proper air-fuel ratio. v i
21. The method of claim 19 further characterized yby and including the kstep of supplying a-sou=rce of air and including the step of' limiting the rate of increase of p the fuel supply when a rapid load 'increase' is 'supplied to the engine.
i12 23. YThe method of Yclaim 19`further characterized' by and including the step `of energizing the auxiliary source Aof energy to supplyadditional energy to the supercharger lICU .during starting of the engine and :at low loads.
24. A system for maintaining an approximately'con- :stant air-fuel ratio in -an engine, an exhaust driven super- 4changer connected to the engine to receive land be driven by the exhaust gases from the eng-ine and to supply yair nnder pressure lto thel engine for combustion therein, a .source of fuel connected to the engine to supply fuel to it, auxiliary means for :supplying additional energy to the :supercharger in addition to theA exhaust energy received by it fromthe engine, and means responsive to an un- -balance between the inlet manifold pressure and the rate at which Vfuel is being supplied Vtothe engine to energize the auxiliary Vmeans to thereby supplyY additional energy to the supercharger. i Y
25. The structure'of claim 24 further characterized .in that the -source `of fuel is gas 'andV the unbalance responsive means is responsive to the relationship between inlet manifold pressure and gas pressure.
26. The structure of claim 24 further characterized` in that the auxiliary means lincludesV a zsource^of airnnder pressure connected to thesuperchanger.
27. The structure ylof claim 24 further characterized by land includingl means for Vlimiting Ithe rate of increase of the fuel supply when la rapid load increasel is applied to References Cited in the le of this patent UNITEDSTATES PATENTS 2,379,455 Prince July'3, 1945 2,533,714 Coar Dec. 12,'19'50 2,608,051 Nettel Aug. 26, 1952 2,620,621 Nettel Dec.'9, 1952 2,893,366 Nystrom July 7, 1959 2,921,431 Sampietro Jan. 19, y1960
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|U.S. Classification||60/606, 60/611|
|Cooperative Classification||F02D9/00, F02D2700/0271|